Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
  • B64C1/1476—Canopies; Windscreens or similar transparent elements
  • B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C33/00—Moulds or cores; Details thereof or accessories therefor
  • B29C33/0011—Moulds or cores; Details thereof or accessories therefor thin-walled moulds
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C33/00—Moulds or cores; Details thereof or accessories therefor
  • B29C33/0038—Moulds or cores; Details thereof or accessories therefor with sealing means or the like
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
  • B32B17/06—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material
  • B32B17/10—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin
  • B32B17/10005—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing
  • B32B17/10009—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the number, the constitution or treatment of glass sheets
  • B32B17/10036—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the number, the constitution or treatment of glass sheets comprising two outer glass sheets
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
  • B32B17/06—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material
  • B32B17/10—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin
  • B32B17/10005—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing
  • B32B17/10165—Functional features of the laminated safety glass or glazing
  • B32B17/10174—Coatings of a metallic or dielectric material on a constituent layer of glass or polymer
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
  • B32B17/06—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material
  • B32B17/10—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin
  • B32B17/10005—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing
  • B32B17/1055—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the resin layer, i.e. interlayer
  • B32B17/10761—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the resin layer, i.e. interlayer containing vinyl acetal
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
  • B32B17/06—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material
  • B32B17/10—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin
  • B32B17/10005—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing
  • B32B17/10009—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the number, the constitution or treatment of glass sheets
  • B32B17/10036—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the number, the constitution or treatment of glass sheets comprising two outer glass sheets
  • B32B17/10045—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the number, the constitution or treatment of glass sheets comprising two outer glass sheets with at least one intermediate layer consisting of a glass sheet
  • B32B17/10055—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of synthetic resin laminated safety glass or glazing characterized by the number, the constitution or treatment of glass sheets comprising two outer glass sheets with at least one intermediate layer consisting of a glass sheet with at least one intermediate air space
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers

Definitions

• This invention relates generally aircraft windows and, more particulariy, to deformabie aircraft cabin windows providing improved aerodynamics and lower drag.
• Aircraft cabin windows are typically made of stretched acrylic.
• the cabin windows are installed n a frame attached to the aircraft fuselage.
• Conventional cabin windows typically have a semi-cylindrical cross-section in which the curved outer surface matches the outer curvature of the aircraft fuselage to provide a smooth outer surface of the aircraft. This reduces drag and promotes in® overall aerodynamics of the aircraft.
• the cabin window can bulge or bow outwardly due to the pressure differential. This causes the outer surface of the cabin window to extend beyond the curvature of the aircraft fuselage, which creates an undesirable aerodynamic drag on the aircraft. This increased drag translates into increased fuel costs and lower cruising speeds.
• This cabin window bulging can be reduced by using relatively heavy and rigid glass windows, which are stronger and less susceptible to bulging than thinner acrylic windows, or by increasing the thickness of the acrylic window to increase its strength and reduce the bulging.
• both of these solutions result in an increased weight penalty, which translates Into lower fuel efficiency.
• a deformabie aircraft window assembly comprises a first panel having a first surface and a second surface, in a first state in which there is no pressure difference between the first surface and the second surface, the first panel has a first cross-sectional shape. In a second state in which there is a pressure difference between the first surface and the second surface, the first panei has an outwardly convex cross-sectionai shape.
• the first cross-sectionai shape of the first panel is seiected from planar, outwardly convex, and inwardly convex.
• a second pane! can be spaced from the first panel.
• the first panei can be a cast pofyurefhane panei.
• the first panel can comprise a buibous peripheral edge configured to engage a receiver in a mounting frame.
• the first panei can have a substantially rectangular peripheral cross-section, wherein the first panel engages a frame such that the outer surface of the first panel is offset from an outer contour of an aircraft fuselage,
• the first panel can have a stepped peripheral edge configured to engage a mounting frame such that the outer surface of the first panel is offset from an outer contour of an aircraft fuselage.
• the first panel and/or second panel can include at least one throughbore.
• the first panel can include at least one cast mounting hole located adjacent a peripheral edge of the first panei.
• the first panel can comprise an angled peripheral edge, wherein the angled peripheral edge engages a seal.
• the seal can be adhesively bonded to a frame.
• a flexible wire can be embedded n the seal,
• the window assembly can include a peripheral gasket.
• An inner edge portion of the peripheral gasket can be embedded in the first panel and an outer peripheral edge portion of the gasket extends beyond the peripheral edge of the first panei,
• the gasket can include at least one hole or throughbore in the inner edge portion of the gasket embedded in the first panei.
• the gasket can include at least one mounting hole located in the outer edge portion of the gasket extending beyond the peripheral edge of the first panel.
• a wire grid can be embedded in the first panel,
• the wire grid can comprise nano-wires.
• the first panel can be an outer panel and the second panel can be an inner panel.
• a functional coating can be located on at least one surface of the first panel and/or the second panel.
• the functional coating can be a solar control coating.
• a protective coating can be located over the functional coating.
• the window assembly can comprise a transparent, compressible material positioned between the first panel and the second panel.
• the compressible material can be in contact with the first panel and the second panel such that there is no air gap between the first panel and the second panel.
• the second panel can include a substantially flat outer surface or outer surface portion.
• An electrochror ic assembly can be located on the outer surface ore outer surface portion of the second panel.
• the first panel can have a thickness variation across a width of the first panel
• the window assembly can include a gradient coating located on at least one surface of the first panel.
• the second panel can have a thickness variation across a width of the second panel
• the window assembly can include a gradient coating located on at least one surface of the second panel.
• the first panel has a planar first cross-sectional shape.
• the first panel has an outwardly convex first cross-sectional shape.
• the first panel has an inwardly convex cross-sectional shape.
• the second panel has a planar first cross-sectional shape.
• the second panel has an outwardly convex first cross- sectional shape.
• the second panel has an inwardly convex cross- sectional shape.
• Fig, 1 is side, sectional view of an aircraft window assembly of the invention in a first state
• Fig. 2 is a side, sectional view of the window assembly of Fig. 1 in a second
• Fig. 3 is a side, sectional view of a casting mold for making an aircraft window panel of the invention
• Fig. 4 is a side, sectional view of an aircraft window assembly of the invention mounted i a frame;
• Fig, 5 is a side, sectional view of an aircraft window assembly of the Invention mounted in a frame using an offset mounting configuration
• FIG. 8 is a detailed view of the lower portion of the aircraft window assembly of Fig. 5;
• F g. 7 is a side, sectional view of the lower portion of an aircraft window assembly similar to Fig, 8 but with an alternative offset mounting configuration;
• FIG. 8 Is a side, sectional view of a further aspect of an aircraft window assembly of the invention.
• FIG. 9 is a plan view of an aircraft window of the invention.
• Fig. 10 is a side, sectional view of a peripheral edge of the aircraft window of
• Fig. 1 1 is a plan view of an aircraft window of the invention having an outer
• Fig. 12 is a side, sectional view of a portion of the aircraft window of Fig. 11 mounted to an aircraft;
• FIG. 13 is a plan view of an aircraft window of the invention incorporating a peripheral gasket
• Fig. 14 is a side, sectional view of a peripheral edge of the window of Fig. 13 attached to a frame;
• FIG. 15 is a plan view of an aircraft window of the invention incorporating a wire grid
• Fig. 16 is a side, sectional view of the aircraft window of Fig. 15;
• Fig. 17 is a side, sectional view of an aircraft window assembly of the invention (frame not shown) incorporating an outer coating;
• FIG. 18 is a side, sectional view of an aircraft window assembly of the invention (frame not shown) incorporating an inner coating;
• Fig. 19 is a side, sectional view of an aircraft window assembly of the invention (frame not shown) incorporating an intermediate compressible material;
• FIG. 20 is a side, sectional view of an aircraft window assembly of the invention (frame not shown) incorporating an eiecfrochromic assembly;
• FIG. 21 is side, sectional view of an aircraft window of the invention
• Fig. 22 is side, sectional view of an aircraft window of the invention
• film refers to a region of a coating having a desired or selected composition
• a “layer* comprises one or more "films”
• a “coating” or “coating stack” is comprised of one or more "layers”.
• over means "on or above”.
• a coating layer "formed over” a substrate does not preclude the presence of one or more other coating layers located between the formed coating layer and the substrate.
• polymer or “polymeric” include oligomers, homopolymers, copolymers, and terpolymers, e.g., polymers formed from two or more types of monomers or polymers.
• visible region or 'Visible light 8 refer to electromagnetic radiation having a wavelength in the range of 380 nanometers (nm) to 780 mm.
• Infrared region or “infrared radiation” refer to electromagnetic radiation having a wavelength in the range of greater than 780 nm to 100,000 nm.
• ultraviolet region or “ultraviolet radiation” mean electromagnetic energy having a wavelength in the range of 100 nm to less than 380 nm.
• the present invention relates to aircraft cabin windows (window assemblies) of the type that are normally used in commercial aircraft.
• the invention comprises, consists of, or consists essentially of the following features, in any combination.
• an aircraft window assembly 10 comprises a transparent first panel 12 (outer panel) having a first surface 14 (outer surface) and a second surface 16 (inner surface).
• the assembly 10 may include an optional second panel 18 ⁇ inner panel) spaced from the first panel 12 and having a third surface 20 (outer surface) and a fourth surface 22 (inner surface).
• an air gap 24 is present between the first panel 12 and the second panel 18.
• the peripheries of the first panel 12 and second panel 18 are fitted within a mounting arrangement, such as a frame 28.
• An elastomeric seal 28 is located around the periphery of the assembly 10.
• the assembly 10 is mounted on an aircraft having a fuselage 30 with an outer surface 32 defining an outer fuselage contour 34 (shown in dashed lines in Fig. 1).
• the cabin 36 of the aircraft is pressurized.
• the first panel 12 is designed to withstand the pressure difference between the relatively higher pressure inside of the aircraft cabin 36 and the lower pressure outside the aircraft at high altitudes, in the aspect shown in Figs, 1 and 2, to allow the first panel 12 rather than the second panel 18 to handle this pressure differential, one or more small holes 38 are provided through the second anel 18 to equalize the pressure between the air gap 24 and the aircraft cabin 38,
• the first pane! 12 of the window assembly 10 has a flat configuration (i.e., planar or substantially planar cross-sectional shape) when there is no or substantially no difference between the pressure in the cabin 36 and the pressure exterior to the aircraft (i.e., an unpressurized or "first" state).
• planar cross-section is meant that the panel 12 lies in a single plane when viewed in cross-section.
• the first panel 12 is closer to the second panel 18 at or near the central region (mediaS region) of the assembly 10 than at the peripheral edges of the assembly 10.
• the outer surface 14 of the first panel 12 is spaced from or offset from the defined fuselage contour 34, with this offset being greater in a central region of the first panel 12 than at the periphery of the first pane! 12.
• the first pane! 12 can have an outwardly convex cross-section in the first state.
• outwardly convex is meant that the medial portion of the first pane! 12 extends further outwardly than the periphery of the first pane! 12.
• the first pane! 12 can have an inwardly convex cross- section in the first state.
• Inwardly convex is meant that the medial portion of the first panel 12 extends further inwardly than the periphery of the first pane! 12.
• the second pane! 18 may also have a planar or substantially planar cross- sectional shape (like the first panel 12 ⁇ in the first state.
• the second panel 18 may have an outwardly convex cross-sectional shape in the first state.
• the second panel 18 may have an inwardly convex cross-sectional shape in the first state.
• the first pane! 12 deflects outwardly such that the contour of the outer surface 14 of the first panel 12 changes from the planar first profile in Fig, 1 to the outwardly convex second profile shown in Fig. 2.
• the outer surface 14 of the first pane! 12 generally approaches or matches the defined contour 34 of the outer surface 32 of the fuselage 30.
• the outer panel 12 can have an outwardly convex contour when in the unpressurized state, i.e. have a surface contour between a flat outboard contour and the curved (outwardly convex shape) shown n Fig. 2.
• the first panel 12 and the second panel 18 may have the same or substantially the same cross- section curvature.
• first panel 12 and/or second pane! 18 can be formed from an initially flat billet and formed to the required shape by a combination of pressing, heating, and/or stretching, it is also contemplated that the first panel 12 and/o the second panel 18 can be oversized and subsequently shaped and cut to a final desired peripheral configuration.
• the first panel 12 and/or second panel 18 can also be cast-to-shape so that little or no post-forming processing is required.
• cast-to-shape is meant that the material for making the panel is poured or injected into a mold such that upon curing or cooling, the cast panel has the desired features already present (e.g., particular edge shape or holes) such that little or no additional manufacturing steps (such as milling, grinding, cutting, or drilling) are required.
• the cast panel is essentially in its final desired form for use in the window assembly,
• plastic materials such as acrylic polymers, such as polyacrylates; polyalkylrnethacryiafes, such as polymethylmethacrylates,
• the first panel 12 and second panel 18 are preferably transparent to visible light.
• transparent is meant having visible light transmission of greater than 0% up to 100%.
• one or both of the panels 12, 18 can be translucent.
• translucent is meant allowing
• electromagnetic energy e.g., visible light
• diffusing this energy such that objects on the side opposite the viewer are not clearly visible.
• the first panel 12 and/or the second panel 18 are made of a transparent material that can be cast and/or formed to the final desired shape, such as but not limited to glass, acrylic, polycarbonate, polyurethane, or other plastics, such as the material made by PPG Industries, Inc., under the trade name OPTICOR, which is a caslable polyurethane material (described in US Publication No. 2013/009531 1 A1 ).
• the first panel 12 is made from a cast polyurethane material.
• both the first panel 12 and the second panel 18 are made of a cast polyurethane material.
• the first panel 12 preferably has a visible light transmitfance of at least 50 %, such as at least 60% ; such as at least 70%, such as at least 80%.
• the second panel 18 preferably has a visible light transmitfance of at ieast 50
• % such as at least 80%, such as at least 70%, such as at least 80%.
• the window assembly 10 preferably has a visible light transmitfance of at least 50 %, such as at ieast 80%, such as at least 70%, such as at least 80%.
• One method of configuring the first panel 12 so that it deflects outwardly the correct amount so that its outer surface 14 matches the aircraft outboard fuselage profile 34 when the aircraft cabin 38 is a pressurized is to vary the thickness of the first panel 12 to make it more or less rigid, as required.
• varying the thickness may lead to optical distortion when viewing through the first panel 12.
• first panel 12 is initially inwardly convex (I.e. outwardly concave), fiat, or outwardly convex (i.e. inwardly concave)
• the thickness of the first panel 12 remains substantially constant throughout the entire viewing area of the first panel 12.
• the periphery of the first panel 12 is provided with a configured edge, e.g. a rabbeted edge 40, which is fitted into a configured edge, e.g. a rabbeted edge 40, which is fitted into a configured edge, e.g. a rabbeted edge 40, which is fitted into a configured edge, e.g. a rabbeted edge 40, which is fitted into a configured edge, e.g. a rabbeted edge 40, which is fitted into a
• This rabbeted edge 40 can be machined about the periphery of the first panel 12 after the first panel 12 has been shaped, e.g., bent, and, if required, cut to shape.
• the rabbeted edge 40 can also be cast to a desired shape when casting the first panel 12, so that post forming processing of the first panel 12 is minimized.
• upper and lower casting molds 44, 48, respectively, along with edge blocks 48, 50 form a cavity into which liquid polymer material 52 is poured, injected or otherwise fed into the cavity to cast the final desired shape of first pane! 12.
• the inwardly directed faces 54, 58 of the casting molds 44, 48 can be made of metal, glass, or any other material that can impart smooth ! undistorted surfaces on the opposing surfaces of first panel 12.
• the edge blocks 48, 50 can be a metal or eiastomeric material, in the one aspect of the invention shown on the left-hand side of Fig. 3, the edge block 48 forms a straight edge along the periphery of the cast panel, which can be subsequently machined to a desired shape (for example as shown by dotted line 58).
• the edge block 50 can be shaped or configured to provide the final desired shape (e.g., rabbited edge 40) of the peripheral edge during casting of the first pane! 12.
• the second panel 18 can be made by the same or different method as the first panel 12.
• the first panel 12 As a monolithic ply, i.e. a single layer structure. It should be appreciated that the first panel 12 can also be a muStiSayered structure, i.e. include two or more plies. In one aspect of the Invention, the first panel 12 is a iaminate having two transparent piles secured together by a thermoplastic adhesive layer, e.g. polyvinyl butyra!, [0082] it is f urther contemplated that the first pane!
• the present invention may include one or more coating layers (as described below) to provide additional functionality to the window assembly 10,
• the outer surface 14 and/or the inner surface 16 of the first panel 2 can incfude an abrasion resistant coating or a UV and/or fR radiation reflecting coating.
• the first panel 12 can include a specially formed curved peripheral edge 58 configured to engage s complementary-shaped receiver 80 in the frame 28,
• the peripheral edge 58 can be a bulbous-shaped projection having an arcuate or partly spherical cross-section.
• the receiver 60 can be a curved groove or channel configured to receive or engage the bulbous projection to capture the peripheral edge 58 of the first panel 12 in the fixed frame 26 and hold the first panel 12 in place.
• a gasket 64 of compressible material can be located in the receiver 80.
• the shape of the peripheral edge 58 defines a notch or groove 68.
• the receiver 80 has an outer tip or projection 88 configured to engage the groove 66,
• the peripheral edge 58 and receiver 60 act as a conventional ball-and-socket joint to hold the first panel 12 in piace.
• the first panel 12 is illustrated as having an outwardly convex cross-sectional shape in the first state.
• the first panel 12 begins to deflect outwardly. Unlike other mounting arrangements in which the peripheral edge of the panel can slide within a peripheral gasket, in the mounting and support arrangement shown in Fig, 4, the periphery of the first panel 12 is fixed in place by the frame 26. This results in the first panel 2 going Into tension as if deflects and the outer surface 14 deflecting outwardly. This tension load resulting from the fixed position of the peripheral edge 58 reduces the deflection of the first panel 12 towards the outboard aircraft profile 34.
• the first panel 12 and material can be selected such that the maximum outward deflection of the first panel 12 generally corresponds with, and in one aspect is essentially coplanar with, the outboard profile 34 of the aircraft fuselage 30.
• the bulbous peripheral edge 58 can twist in the receiver 60.
• the projection 68 engaged In the groove 66 helps to maintain the first panel 12 connected to the frame 26.
• the first panei 12 is manufactured without a shaped peripheral edge (e.g., rabbited edge 40 or curved peripheral edge 58 described above).
• the frame 26 is configured and the first panei 12 is installed into the aircraft such that the outer surface 14 of the first panel 12 is not cop!anar with the outboard profile 34 of the aircraft fuselage 30 when the aircraft is not pressurized (first state).
• the peripheral edge of the first panel 12 is offset from outboard profile 34 of the aircraft fuselage 32 by a distance "X".
• the first panel 12 deflects outwardly, with the centra! portion generally aligned and essentially coplanar with the aircraft outboard profile 34 to reduce the wind drag on the aircraft.
• the outer surface 14 at the periphery of the first pane! 12 remains offset from the aircraft outboard profile 34 at or near the periphery of the first panel 12,
• ft is appreciated that due to the offset X of the first panel 2 at or near the periphery that is maintained during deflection of the first panel 12, eddy currents are created in this perlpherai region of the first panel 12.
• an aiternate aspect of the first panel 12 can be provided with a stepped or rabbeted edge 70. This edge arrangement resuits in the first panel 12 periphery being installed in the aircraft with an offset of ⁇ ", which is less than the offset X shown in Fig. 6.
• the outer surface 14 of the first panel 12 is configured and the first panel 12 is installed into the aircraft such that the outer surface 14 would not be copianar with the outboard profile 34 of the aircraft fuselage 32 when the aircraft is not pressurized, with the peripheral edge of the first panel 12 being offset from the outboard profile 34 of the fuselage 32 by a distance Y.
• the central portion of the first panel 12 deflects outwardly to a position generally aligned and essentially coplanar with the aircraft outboard fuselage profile 34.
• the periphery of the first panei 12 remains offset from the aircraft outboard profile 34 due to the rabbeted edge 70.
• the offset of the first panei 12 periphery shown in Fig. 7 is reduced as compared to Fig. 6, thus reducing the eddy currents created in this peripheral region of the first panel 12, and reducing the accompanying wind drag on the aircraft.
• the frame 26 is not shown for ease of discussion
• the first panel 12 has one or more holes 72 and the second panel 18 does not have the holes 38 described in the above aspects.
• the holes 72 provide for pressure equilibrium between the exterior of the aircraft and the air gap 24.
• the second panel 18, not the first panel 12 is the primary functional barrier between the cabin 36 and the exterior of the aircraft. Irs a pressurized state (second state), shown by dash lines 74 in Fig, 8, the second panel 18 deflects outwardly towards the first pane! 12 due to the pressure difference between the interior and the exterior of the aircraft.
• the first panei .12 can be a rigid panel, such as glass, stretched acrylic, or cast polyurethane.
• the second panel 18 Is a flexible panel, such as east polyurethane, which In a relaxed or unpressurized state can be planar or
• substantially planar in cross-section or can have an outwardly convex contour, or an inwardly convex contour.
• the first panel 12 is a cast
• the polyurethane panel having a plurality cast mounting holes 78 located around the periphery of the panel.
• the mounting holes 76 can be used to attach the first panei 12 to the frame 28, such as by inserting bolts 78 or other fasteners through the mounting holes 78 to mount the first panel 12 to the frame 26.
• the first panel 12 includes an angled peripheral edge forming an angled projection 82 that engages a groove or channel 84 in a flexible sealing member 88 located around the outer periphery of the first panel 12.
• the sealing member 86 can be made of any conventional flexible material, such as polymers or rubber.
• the first panel 12 Is shown attached to the frame 28 by an adhesive layer 88, such as a conventional glue or other suitable adhesive, to adhesively bond the sealing member 88 to the aircraft or aircraft frame 28.
• the sealing member 86 can include a flexible metal wire 90 embedded in the seai material to allow for easier removal of the first panel 12 from the frame 26.
• an end of the wire 90 can stick out of the sealing member 86.
• this outer end of the wire 90 can be pulled. As the wire 90 is pulled, this breaks the sealing member 86 and allows the first panel 12 to be removed more easily.
• a gasket 92 is attached to or embedded in the first panel 12, for example around the outer periphery of the first panel 12.
• first panel 12 is a cast polyurethane material
• an inner edge portion 94 of the gasket 92 can be positioned such that the polyurethane material forms around and over this Inner edge portion 94.
• the inner edge portion 94 of the gasket 92 is thus embedded in the first panel 12.
• the inner edge portion 94 can include a plurality of holes or throughbores 98 such that when the panel is cast, the polyurethane material flows into and through the throughbores 98 and solidifies in these throughbores 96 to anchor the inner edge portion 94 of the gasket 92 in the first panel 12 to help prevent the gasket 92 from being removed or pulled out of the first panel 12.
• An outer peripheral portion 98 of the gasket 92 can include a plurality of mounting holes 100 such that, as shown in Fig. 14, the first panel 12 can be connected to an aircraft or the frame 28 by inserting fastening members, such a bolts 78, through the mounting boles 100 to attach the gasket 92 to the frame 28 to hold the first pane! 12 in piace.
• th ⁇ first panel 12 can also include a wire grid
• This wire grid 102 can be, for example, nano-wires useful for electromagnetic pulse protection,
• the first panef 12 can Include at least one functional coating 104 on the outer surface 14 and/or the inner surface 16.
• the functional coating 104 can be, for example, a conductive coating; solar control coating having one or more infrared reflective metal layers; a protective coating, such as having one or more metal oxide layers, to provide mechanical and/or chemical protection; or an "ernp" coating to provide protection against damage caused by an electromagnetic pulse.
• a protective coating 108 can be placed over the functional coating 104 to protect the functions! coating 104 from chemical and/or mechanical damage during flight.
• suitable protective coatings 106 include metal oxide coatings or polymeric coatings.
• One particularly suitable material is SOLGARD coating ⁇ made by PPG Industries, !nc.)
• the functional coating 104 (or another functional coating) can be located on the Inner surface 16 of the first panel.
• Fig. 18 shows an aspect of the window assembly 10 of the invention having a functional coating 104 on the second panel 18.
• the functional coating 104 can be as described above.
• Fig, 19 illustrates an aircraft window assembly 10 of the invention in which a compressible material 108 is positioned between the first panel 12 and the second panel 18.
• a compressible material 108 is positioned between the first panel 12 and the second panel 18.
• no air gap 24 is present between the first panel 12 and the second panel 18.
• the second panel 18 deflects outwardly and presses against the compressible material 108.
• the compressible material 108 absorbs at least some of this outward deflection of the second pane! 18 to help reduce the outward deflection of the first panel 12.
• the compressible material 108 is preferably a transparent material.
• suitable compressible materials 108 include transparent, compressible polymers. Particular examples include plastic materials such as acrylic polymers, urethane polymers, and vinyl polymers. One particular exemplary material is polyvinyl butyral.
• Fig. 20 illustrates an aircraft window assembly 10 of the invention having an elecirochromic assembly 110, in the illustrated aspect, the electrochromic assembly 110 is located on the second panel 18.
• the second panel 18 can have a planar cross-sectional shape in this aspect or at least a portion of the second panel 18, such as the central or medial portion of the second panel 18, can have a flat surface on which the eSectroehromic assembly 110 can be located.
• the electrochromic assembly 110 can be any conventional electroehromic device having a material that reversibly changes color (e.g., lightens and darkens) when an electrical potential Is applied or removed.
• F g. 21 illustrates an aircraft window assembly 10 of the invention in which the first panel 12 has a thickness variation across a length or width of the panel. It is believed this thickness variation can help counteract the fensing effect caused by the deflection of the psnei(s) 12, 18 of the aircraft window assembly 10.
• the first panel 12 is thicker at the periphery and thinner toward the center.
• the first panel 12 could be thinner at the periphery and thicker toward the center,
• the second panel 18 can have a thickness variation across a length or width of the panel, as described above with respect So the first panel 12.
• the second panel 12 can be thicker at the periphery and thinner toward the center.
• the second panel 12 couid be thinner at the periphery and thicker toward the center,
• Fig. 22 illustrates an aircraft window assembly 10 of the invention having a gradient coating 112 located on the first panel 12.
• the gradient coating 112 is located on the outer surface 14 of the first panel 12.
• This gradient coating 112 (or another gradient coating) could alternatively be located on the inner surface 18.
• the gradient coating 112 has a thickness variation across a length or width of the gradient coating 112.
• the gradient coating 112 is thicker at the periphery and thinner toward the center.
• the gradient coating 112 could be thinner at the periphery and thicker toward the center. This gradient coating 112 can help counteract the tensing effect caused by the deflection of the panel(s) of the aircraft window assembly 10.
• a gradient coating 112 can be located on the third surface 20 and/or fourth surface 22 of the second panel 18, The gradient coating 112 can have a thickness variation across a length or width of the gradient coating 1 12.
• the gradient coating 112 can be thicker at the periphery and thinner toward the center.
• the gradient coating 1 2 could be thinner at the periphery and thicker toward the center.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• Securing Of Glass Panes Or The Like (AREA)
• Laminated Bodies (AREA)
• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)

Priority Applications (8)

Applications Claiming Priority (4)

Publications (2)

Family

ID=52465795

Family Applications (1)

Country Status (8)

Cited By (3)

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Citations (1)

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• 2014
  • 2014-08-05 CA CA2918253A patent/CA2918253C/en active Active
  • 2014-08-05 EP EP14838885.3A patent/EP3030485B1/de active Active
  • 2014-08-05 RU RU2016108019A patent/RU2631152C2/ru active
  • 2014-08-05 EP EP18167192.6A patent/EP3372489B1/de active Active
  • 2014-08-05 US US14/451,857 patent/US10202183B2/en active Active
  • 2014-08-05 EP EP20152806.4A patent/EP3677501A1/de not_active Withdrawn
  • 2014-08-05 BR BR112016002283A patent/BR112016002283A2/pt not_active Application Discontinuation
  • 2014-08-05 ES ES18167192T patent/ES2774273T3/es active Active
  • 2014-08-05 ES ES14838885.3T patent/ES2674550T3/es active Active
  • 2014-08-05 CN CN201480044458.5A patent/CN105452102B/zh active Active
  • 2014-08-05 WO PCT/US2014/049747 patent/WO2015069339A2/en not_active Ceased

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